Zobrazeno 1 - 5
of 5
pro vyhledávání: '"A. Yu. Noev"'
Publikováno v:
AIP Conference Proceedings.
Boundary-layer transition on slender blunt cone in hypersonic flow at zero incidence is under investigation. Main attention is paid to relatively large nose radius values when so-called transition reversal phenomenon is observed. Analysis of publishe
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::dc3f5580f308c97154d004fd72bc0047
https://doi.org/10.1063/1.5065205
https://doi.org/10.1063/1.5065205
Autor:
Alexander D. Kosinov, A. Yu. Noev, A. S. Skuratov, Vladimir Nikolaevich Radchenko, A. V. Vaganov
Publikováno v:
AIP Conference Proceedings.
Experiments were conducted at Mach number 6 in UT-1M Ludwieg tube. The model is flat delta plate with blunt swept (χ=75-67°) edges and sharp tip. Surface heat transfer distributions were obtained using luminescent temperature converters. Characteri
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::5ed7f8740ddb6e577625343daa8aba8d
https://doi.org/10.1063/1.5065206
https://doi.org/10.1063/1.5065206
Autor:
A. V. Vaganov, V. I. Shalaev, D. V. Grachikov, V. M. Kashin, Vladimir Nikolaevich Radchenko, A. S. Skuratov, V. D. Nemykin, A. Yu. Noev
Publikováno v:
AIP Conference Proceedings.
The paper deals with laminar-turbulent transition in the vicinity of blunt leading edges of flat delta wing in hypersonic flow. Under investigation is influence of wing nosetip shape, Reynolds number, angle of sweep and attack on transition onset and
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::9f3325be9263eed0e99481f47c8772df
https://doi.org/10.1063/1.5007528
https://doi.org/10.1063/1.5007528
Autor:
A. S. Skuratov, V. I. Plyashechnik, A. A. Shustov, Vladimir Nikolaevich Radchenko, A. Yu. Noev, A. V. Vaganov
Publikováno v:
AIP Conference Proceedings.
Influence of flow parameters and nose radius on laminar-turbulent transition location is under investigation. Experiments were conducted in shock tunnel at Mach number 6. Transition location was diagnosed by heat transfer rate distribution determined
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::6293b713ed50f9966c668a2630e17063
https://doi.org/10.1063/1.4963991
https://doi.org/10.1063/1.4963991
Publikováno v:
Fluid Dynamics. 46:917-934
The results of an experimental and numerical investigation of flow and heat transfer in the region of the interaction between an incident oblique shock and turbulent boundary layers on sharp and blunt plates are presented for the Mach numbers M∞ =
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::7054b0a6e8d54f29440c0960eac94cf8
https://doi.org/10.1134/s0015462811060093
https://doi.org/10.1134/s0015462811060093